High strength joints in ceramic matrix composite preforms

ABSTRACT

A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.

TECHNICAL FIELD

The present disclosure generally relates to joined composite preforms such as ceramic matrix composite preforms useful to produce a gas turbine engine component, and more particularly, but not exclusively, to a joint used to join the composite preforms.

BACKGROUND

Providing joined structures with adequate performance at the joint such as shear, pull out strength, and toughness remains an area of interest. Some existing systems have various shortcomings relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology.

SUMMARY

One embodiment of the present disclosure is a unique joint structure for composite preforms. Other embodiments include methods for constructing the aforementioned joint structure. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 is a cross-sectional schematic view of a gas turbine engine.

FIG. 2 Illustrates a preform component with extended fibers.

FIG. 3 depicts a preform component with stiffened internal fibers.

FIG. 4 shows a preform component joined to another preform component, with fibers extending from one preform component into the other.

FIG. 5 represents a preform component joined to another preform component, with fibers extending from both preform components into one another.

FIG. 6 illustrates two preform components joined together with fibers extending from one preform component through the other preform component.

FIG. 7 depicts two joined preform components with fibers extending partially through each preform component.

FIG. 8A-8D illustrate various embodiments of joints created between preform components lying in distinct planes.

FIG. 9 depicts an embodiment of joints created between multiple preform components lying in multiple distinct planes.

DETAILED DESCRIPTION OF THE ILLUSTRATIVE EMBODIMENTS

For purposes of promoting an understanding of the principles of the disclosure, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended. Any alterations and further modifications in the described embodiments, and any further applications of the principles of the invention as described herein are contemplated as would normally occur to one skilled in the art to which the invention relates.

Referring to FIG. 1, a schematic view of a gas turbine engine 10 is depicted. While the gas turbine engine is illustrated with two spools, it should be understood that the present invention is not limited to any particular engine design or configuration and as such may be used in single or multi spool engines. The gas turbine engine 10 will be described generally, however significant details regarding general gas turbine engines will not be presented herein as it is believed that the theory of operation and general parameters of gas turbine engines are well known to those of ordinary skill in the art.

The gas turbine engine 10 includes an inlet section 12, a compressor section 14, a combustor section 16, a turbine section 18, and an exhaust section 20. In operation, air is drawn in through the inlet 12 and compressed in the compressor section 14 to a high pressure relative to ambient pressure of the gas turbine engine 10. The compression section 14 includes plurality of stages with rotating blades 22 that operate to compress working fluid and vanes 24 positioned upstream of a rotating blade 22 to control aerodynamic properties of the working fluid entering into the rotating stage.

The compressed air is mixed with fuel in the combustor section 16 wherein the fuel/air mixture burns and produces a high temperature and pressure working fluid from which the turbine section 18 extracts power. The turbine section 18 is mechanically coupled to the compressor section 14 via a shaft 21, which rotates about a centerline axis X that extends axially along the longitudinal axis of the engine 10. As the turbine section 18 rotates due to the forces generated by the high pressure working fluid, the compressor section 14 is rotatingly driven by the turbine section 18 via the shaft 21 to produce compressed air. A portion of the power extracted from the turbine section 18 can be utilized to drive a second device 23 through a second shaft 25, such as a fan, an electrical generator, gas compressor or pump and the like.

Many composite components utilized within a gas turbine engine may be made of a ceramic matrix composite (“CMC”), as they are suitable for operational use in the high pressure and high temperature internal operating environment of a gas turbine engine. CMCs will be described generally, however significant details regarding CMC formation and manufacture will not be presented as it is believed that the general aspects of CMC manufacturing are well known to those of ordinary skill in the art. It is appreciated that while general aspects of CMC manufacturing are disclosed in the present application, many variations in the processes and materials used are envisioned in the present application and no limitation of the scope of the invention is thereby intended.

CMCs are first made from a lay-up of a plurality of fibers and formed to a desired shape. At this stage in the production of a CMC component, the lay-up is generally known as a fiber preform or preform. The fiber preform can be can be partially-rigidized or un-rigidized and can be constructed in any number of different configurations, for example, the preform may be made of filament windings, braiding, and knotting of fibers, as well as made of two-dimensional and three-dimensional fabrics, unidirectional fabrics, and non woven textiles. The fibers used in the preform, furthermore, can be made from any number of the materials such as, but not limited to, ceramic fibers, organic fibers, metallic fibers, and glass fibers. The preform can be of near-net shape and/or machined and/or undergo further treatments such as coating or impregnation of the matrix material.

During construction of the CMC the fiber arrangement can be infiltrated with a matrix material. The matrix can be made of any number of materials such as, but not limited to, polymers, metals, and ceramics, such as silicon carbide, and silicon/silicon carbide. The preform can be infiltrated with the matrix using any number of processes such as, but not limited to deposition from a gas phase, such as chemical vapor deposition or chemical vapor infiltration, pyrolysis, chemical reaction, sintering, and electrophoresis. Finally, the part may be machined, if necessary to bring the part geometry into the required specifications.

With reference to FIG. 2, an example fiber preform component 100 is provided with a main body 102 that includes a plurality of interwoven body fibers. The plurality of interwoven body fibers may be a two-dimensional or three-dimensional weave, or any of the above-mentioned fabrics. For clarity, these interwoven body fibers are not shown in any of the figures. However, it is appreciated that the preforms disclosed herein may contain such fibers. It is assumed that these types of fibers are readily apparent to those skilled in the art, and the focus of the disclosure will center on the extended fibers 104, 204 discussed in more detail herein.

The main body 102 also includes an end surface 106, which in some of the illustrated embodiments discussed herein is used to be engaged in proximity to an adjacent preform component. A plurality of fibers are configured as extended fibers 104 which can be integrally provided within, or at least partially integrated or embedded within, the body 102, and have an extended or protruding portion that protrudes away from the end surface 106. The extended fibers 104 may be disposed within the interstices of the interwoven body fibers of the body 102. The extended fibers 104 can but need not be the same type as the interwoven body fibers. The plurality of extended fibers 104 may be bundled or single monofilaments, and may even be a single bundle. The plurality of extended fibers 104 may be varied in length and spacing. In addition, the extended fibers 104 may also, but not necessarily, extend out of the surface opposite the end surface 106 similar to that shown in FIG. 2. Furthermore, the fiber preform component 100 may be infiltrated with a matrix.

With reference to FIG. 3, another example preform component is illustrated in which the fibers 104 are initially contained within the main body 102 of the preform but, through a manufacturing operation, at least a portion of the main body 102 is compressed resulting in the fibers 104 being exposed and protruding from the main body 102. The preform is made of a plurality of interwoven body fibers (not shown) and includes an end surface 106. A plurality of fibers 104 are integrally provided within or at least partially integrated or embedded within the main body 102.

The plurality of fibers 104 may be extended out of the main body 102, through the end surface 106, by compressing the body 102 and thereby compressing the interwoven body fibers that are less stiff than the plurality fibers 104 that remain. The extended fibers 104 in the illustrated embodiment tend to be more rigid than the interwoven body fibers of the body 102, such that the interwoven body fibers of the body 102 are more compliant than the extended fibers 104. It is appreciated that only a portion of the body 102 or the entire body 102 may be compressed. The body 102 only needs to compress enough for the extended fibers 104 to sufficiently extend through the end surface 106. The body 102 may be compressed as the end surface 106 is pressed against a second preform component 200, as described in greater detail herein. As is shown, the end surface 106 of the uncompressed body 102 is shown as a solid line and the end surface 106 of the compressed body 102 is shown as a dashed line.

Referring to FIGS. 4-7, example apparatuses 50 are provided by joining a first preform component 100 to a second preform component 200. The first preform component 100 is provided with a main body 102, made of a plurality of interwoven body fibers (not shown), and having an end surface 106. A plurality of extended fibers 104 are integrally provided within or at least partially integrated or embedded within the body 102 and have an extended portion that extends or protrudes through and away from the end surface 106. The second preform component 200 is also provided with a main body 202 made of a plurality of interwoven body fibers (not shown) and having an end surface 206. End surfaces 106, 206 are brought together and a joint is created at this interface. At least a portion of the extended fibers 104 extend into and are enveloped by the body 202 of the second preform component 200. The fibers 104 can be received within a space of the second preform component 200 such that the fibers 104 are not in contact with any fibers of the second component 200, but in some embodiments any or all of the fibers 104 can contact one or more fibers of the second component 200. The extended fibers 104 may be received within a preformed opening in the second component 200, or within the interstices of the second component's body fibers (not shown).

Various means may be provided to ease or aid insertion of the extended fibers into a preform. For example, a fibrous reinforcement that is accepting extended fibers may be locally altered to reduce the fiber volume to ease insertion, or to tailor local mechanical properties, or to aid with matrix processing. The preform component 200 accepting the fibers 104 may also include or be supplied with interstitial openings (not shown) spaced to correspond with the spacing of the plurality of extended fibers. This may ease insertion, provide registration of the preforms, and improve the strength of the joint. In addition, one or more lubricants may be utilized to ease the insertion process and reduce fiber damage during insertion, as well as to reduce buckling loads on the fibers and the required insertion force. Ultrasonic vibration may also be used to aid in insertion of the fibers.

Appropriate tooling and/or fixtures may be necessary to provide proper support of the preform components as they are pressed together, and to prevent long fibers from buckling during and to ease insertion. To further aid in the prevention of fiber buckling, a low strength polymer may be cast over the fibers such that as force is applied, and the extended fibers are inserted into the other preform component, the polymer is progressively extruded from the joint. Removable fixturing may also serve the same purpose.

With specific reference to FIG. 4, as the joint is created and the end surfaces 106, 206 are brought together, the plurality of extended fibers 104 penetrate the end surface 206 and into the body 202 of the second preform component 200. Thus, the second preform component 200 envelopes and defines an extended portion of the extended fibers 104. To further strengthen this joint, one or more laminate strips 150 may be disposed about or applied to this joint.

Referring now to FIG. 5, the second preform component 200 is provided with a second plurality of extended fibers 204 integrally provided within or at least partially integrated or embedded within the body 202 and have an extended portion that extends through and away from the end surface 206. As the joint is created and the end surfaces 106, 206 are brought together, the first plurality of extended fibers 104 penetrate the second end surface 206 and into the body 202 of the second preform component 200, and the second plurality of extended fibers 204 penetrate the first end surface 106 and into body 102 of the first preform component 100. Thus, the second preform component 200 envelopes and defines an extended portion of the first plurality of extended fibers 104, and the first preform component 100 envelopes and defines an extended portion of the second plurality of extended fibers 204. To further strengthen this joint, one or more laminate strips (not shown) may be disposed about this joint.

The extended fibers of either or both the first preform 100 and second preform 200, and/or either or both of the first and second preforms 100, 200 can be created, inserted, extended, modified, coated, treated, manipulated, etc according to any of the description above.

With specific reference to FIG. 6, as the joint is created and the end surfaces 106, 206 are brought together, the plurality of extended fibers 104 penetrate the end surface 206 and extend entirely through the body 202 of the second preform component 200. Thus, the second preform component 200 at least partially envelopes and defines an extended portion of the extended fibers 104. To further strengthen this joint, one or more laminate strips (not shown) may be disposed about this joint. The extended fibers of the preform 100, and for that matter either of the preforms 100 and 200, can be created, inserted, extended, modified, coated, treated, manipulated, etc according to any of the description above.

With reference to FIG. 7, a joint is created at an interface between the end surfaces 106, 206. As this joint is created and the end surfaces 106, 206 are brought together, the plurality of extended fibers 104 penetrate the end surface 206 and into the body 202 of the second preform component 200. Thus, the second preform component 200 envelopes and defines an extended portion of the extended fibers 104. To further strengthen this joint, one or more laminate strips (not shown) may be disposed about this joint. A difference between this embodiment and those shown and described in FIGS. 4-6, is that the set of fibers 104 are only located at or near the joint, and not necessarily continuous throughout the entire first preform body 102. The fibers 104 can be inserted into the body 202 or can be formed simultaneous with other fibers (not shown, but similar in some embodiment to the fibers shown in FIG. 5) that are formed together in the body. The first preform body 102 can be infused with polymers or other materials to hold the extended fibers 104 in place during insertion of the fibers 104. It is appreciated that this infusion process may also be utilized in the other examples discussed herein. Furthermore, the fibers 104, and for that matter either of the preforms 100 and 200, can be created, inserted, extended, modified, coated, treated, manipulated, etc according to any of the description above.

In any of the embodiments shown in FIGS. 4-7 and described in their associated text, the extended fibers 104, 204 may extend prior to joining the two preform components 100, 200, or be extended during fabrication of the joint by compressing the respective bodies 102, 202 (see Ha 3), as described herein. It is appreciated that to be integral with or embedded within their preform, the plurality of extended fibers may be continuous through the form or be present just adjacent to the joint, as is shown in FIG. 7. Penetration depth of the fibers may range from 0.010 inches to the entire thickness and even through the other form. The fibers may uniformly extend or protrude from a form, or may include some local variation in extension from the form for any variety of reasons. In addition, the extended length of the fibers may also vary locally (see FIG. 2). Though only two preform components 100, 200 are shown in the above described embodiments, it is appreciated that more than two preform components may be joined together as described herein (see FIG. 9).

The abutting end surfaces 106, 206 are preferably geometrically matched. However they need not lie in a single plane, as the present disclosure envisions the joining of both simple and complex curved surfaces. Furthermore, it is appreciated that when creating the joint between the two preform components 100, 200, the preform components 100, 200 can be at any arrangement relative to one another so long as fiber insertion remains possible. For example, the reform components 100, 200 may be either coplanar or they may be on distinct planes. As used herein, the phrase “distinct planes” may carry a wide range of definitions. This phrase will now be explained in more detail. Referring to FIGS. 8A-8D, a variety of example apparatuses 50 are shown in cross-section with each component lying in a plane. FIG. 9 depicts multiple components in cross-section that lie in multiple and distinct planes. For clarity, the extended or protruding fibers of the present disclosure are not shown in FIGS. 8A-9.

As shown in FIG. 8A, an example apparatus 50 is created by joining two coplanar preform components 100, 200. The preform bodies 102, 202 share a common longitudinal axis 1000 and the surfaces adjacent to the joint 105, 205 also lie on a common plane.

Referring to FIG. 8B, an example apparatus 50 is created by joining two preform components 100, 200. The first preform body 102 has a first longitudinal axis 1000, and the second preform body 202 has a second longitudinal axis 2000 that may intersect with or be skew to the first longitudinal axis 1000 such that the first and second preform bodies 102, 202 lie on intersecting planes distinct and separate from one another. Furthermore, the surfaces 105, 205 adjacent to the joining end surfaces 106, 206 also lie on distinct and separate intersecting planes.

Referring to FIG. 8C, an example apparatus 50 is created by joining two preform components 100, 200. The first preform body 102 has a first longitudinal axis 1000, and the second preform body 202 has a second longitudinal axis 2000 that may orthogonal to the first longitudinal axis 1000. Thus, the first and second preform bodies 102, 202 lie on intersecting planes distinct and separate from one another. Furthermore, the surfaces 105, 205 adjacent to the joining end surfaces 106, 206 also lie on distinct and separate intersecting planes.

Referring now to FIG. 8D, an example apparatus 50 is created by joining two preform components 100, 200. The first preform body 102 has a first longitudinal axis 1000, and the second preform body 202 has a second longitudinal axis 2000 that may parallel or skew to the first longitudinal axis 1000 such that the first and second preform bodies 102, 202 lie on parallel planes distinct and separate from one another. Furthermore, the surfaces 105, 205 adjacent to the joining end surfaces 106, 206 also lie on distinct and separate parallel planes.

With reference now to FIG. 9, another example apparatus 50 is provided by joining three preform components 100, 200, 300. As shown, the first and second preform components 100, 200 are shown as having generally rectangular bodies 102, 202 yet having complexly curved joining end surfaces 106, 206. Though shown as a two-dimensional curve in a cross-section, it is appreciated that the end surfaces may have a complex three-dimensional curved surface. The third preform component 300 is shown as generally having a cross-sectional shape 302 of an airfoil that has a complex three-dimensionally curved joining end surface 306. In this embodiment, the first and second joined preform components 100, 200 may be coplanar, though they may also be in distinct planes, yet the third preform component 300 lies in multiple planes that are distinct and separate from the first and second preform components 100, 200.

The disclosure applies to a variety of fibers such as, for example, one or more of the following: glass, carbon, aramid, ceramic oxide, ceramic nitride, and ceramic carbide. Examples of ceramic carbide may be silicon carbide (“SiC”) such as that sold under the trade name Nicalon and manufactured by the Nippon Carbon Co., Ltd. of Tokyo, Japan. The disclosure also applies to a variety of matrices such as, for example, one or more of the following: polymers, metals, and ceramics such as SiC, and silicon/silicon carbide. The disclosed joint may also prove useful with matrices that exhibit low strength and toughness such as, for example, silicon carbide, alumina, mullite, carbon, silicon, silicon/silicon carbide particulate, untoughened epoxy, polyimide, vinyl ester, and polyester.

The extended fibers may be bundled fibers or monofilaments. Monofilaments such as a SiC fiber sold under the trade name SCS Silicon Carbide Fiber, manufactured by Specialty Materials, Inc. of Lowell, Mass. may be sufficiently stiff and strong enough to withstand insertion and act independently during insertion. Alternatively, the extended fibers may be stiffened through the use of, for example, polymers, metal coatings, or ceramic coatings.

The laminate envisioned in this disclosure include, for example, two-dimensional fabrics, three-dimensional textiles, unidirectional fabrics, or non-woven textiles. The laminate may be, for example, dry, infused or pre-impregnated with binders, particulate, whisker or other fillers. The laminate may also be a unidirectional tape with fibers spread evenly then notched or slit and reshaped for the joint. R is appreciated that the laminate may be one or multiple layers and may be continuous about the joint or only located in one or multiple discrete locations. It is appreciated that a gap filling preform may be applied at the joints between the laminate and the preform components.

An example embodiment of the present disclosure may be utilized in the manufacture of an example hollow ceramic matrix composite vane, as may be used in a typical gas turbine engine. The vane may be pressurized internally while in service and may be made of a SiC/SiC composite. The vane may further be provided with integral endwalls. The top and bottom of the vane preform may be primarily constructed of Hi Nicalon type S fiber and be provided with protruding SCS Ultra fibers that run the full length of the vane preform body and protrude from the ends 0.150 inches. The endwall preforms are laminated independently at 0.180 inches thick.

Each endwall preform may be registered with external tooling. The vane preform may be supported by a temporary polymer binder and an external fixture that is temporarily bonded in place. Each endwall preform is pressed into the vane preform. A deltoid gap filling preform is applied at the joints, and layers of Hi Nicalon fabric may be applied to the deltoid filler and adjacent preforms to reinforce the joints. The joined preforms may be tooled for boron nitride fiber coating by chemical vapor infiltration. The joined preform components may further be infiltrated with SIC by chemical vapor infiltration. The joined preform components may then be densified with a SiC slurry/Si melt infiltration process. The joined preform components may now be machined to the appropriate dimensions and coated with an environmental barrier coating and/or thermal barrier coating.

Another example embodiment of the present disclosure may be utilized in the manufacture of an example solid ceramic matrix composite blade, as may be used in a typical gas turbine engine. A contoured blade preform may be fabricated using Hi Nicalon fabric with a contoured airfoil shape and an attachment feature, such as a dovetail or multi-lobe fir tree design. Two contoured plates may be independently fabricated as platform preforms, each with an edge that matches the contour of the airfoil shape on the blade preform. These edges may further be provided with extending SCS fibers.

All three preform components may be supported by appropriate tooling while the platform preforms are pressed into the blade preform. Layers of Hi Nicalon fabric may be applied from the attachment feature across the lower surface of the platform preforms. Layers of Hi Nicalon fabric with a cutout of the airfoil shape cross-section may also be applied on the upper surfaces of the platform preforms. The layers of Hi Nicalon fabric reinforce the joint from both sides and may extend fore and aft of the blade preform. The joined preform components may be tooled for boron nitride fiber coating by chemical vapor infiltration. The joined preform components may further be infiltrated with SiC by chemical vapor infiltration. The joined preform components may then be densified with a SIC slurry/Si melt infiltration process. The joined preform components may now be machined to the appropriate dimensions and coated with an environmental barrier coating and/or thermal barrier coating.

Yet another example embodiment of the present disclosure may be utilized in the manufacture of a seal segment having an anti-rotation feature. A curved seal segment preform may be fabricated from a simple laminate cross-section using Hi Nicalon fabric. Instead of local thickening or machining a groove or notch into the seal segment, a 0.250 inch wide by 0.500 inch long by 0.250 inch high anti-rotation preform is independently manufactured with polymer rigidized bundles of Hi Nicalon fiber extending 0.125 inches from a surface of the anti-rotation preform.

The curved seal segment and anti-rotation preform may be supported by appropriate tooling while the two preform components are aligned and pressed together. The joined preform components may be tooled for boron nitride fiber coating by chemical vapor infiltration. The joined preform components may further be infiltrated with SIC by chemical vapor infiltration. The joined preform components may then be densified with a SiC slurry/Si melt infiltration process. The joined preform components may now be machined to the appropriate dimensions and coated with an environmental barrier coating and/or thermal barrier coating.

It is appreciated that the above examples are only example embodiments of the present disclosure and that the disclosed dimensions and components may vary. It is further appreciated that many additional embodiments are envisioned for metal matrix and polymer matrix components. Furthermore, while it is envisioned that the joining end surfaces abut one another, a slight gap may exist between these surfaces prior to infiltration and densification.

While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the preferred embodiments have been shown and described and that all changes and modifications that come within the spirit of the inventions are desired to be protected. It should be understood that while the use of words such as preferable, preferably, preferred or more preferred utilized in the description above indicate that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, the scope being defined by the claims that follow. In reading the claims, it is intended that when words such as “a” “an,” “at least one,” or “at least one portion” are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. When the language “at least a portion” and/or “a portion” is used the item can include a portion and/or the entire item unless specifically stated to the contrary.

Unless specified or limited otherwise, the terms “mounted,” “connected,” “supported,” and “coupled” and variations thereof are used broadly and encompass both direct and indirect mountings, connections, supports, and couplings. Further, “connected” and “coupled” are not restricted to physical or mechanical connections or couplings. 

What is claimed is:
 1. An apparatus comprising: a gas turbine engine component construction suitable for operational use in an operating environment associated with a gas turbine engine, the component construction including a first ceramic matrix composite preform component comprising a first end surface and a second ceramic matrix composite preform component comprising a second end surface, the first composite preform component including a plurality of extended fibers having an extended portion that protrudes away from the first end surface, the extended fibers received within an internal space of a body of the second composite preform component such that the body of the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers and creates a joint between the first composite preform component and the second composite preform component at an interface of the first end surface and the second end surface; and wherein the extended fibers are woven into the first ceramic matrix composite preform but not woven into the second ceramic matrix composite preform.
 2. The apparatus of claim 1, wherein the gas turbine engine component construction is a precursor to a ceramic matrix composite component structured for use as an airfoil member in the gas turbine engine.
 3. The apparatus of claim 1, wherein the first composite preform component includes a plurality of body fibers, and wherein the extended fibers protrude only partially into the body of the second composite preform component.
 4. The apparatus of claim 1, wherein the first preform component, the second preform component, and the plurality of extended fibers comprise at least one material selected from the group consisting of glass, carbon, aramid, ceramic oxide, ceramic nitride, and ceramic carbide; and wherein the first preform component and the second preform component comprise a matrix comprising at least one material selected from the group consisting of polymers, metals, silicon carbide, and silicon/silicon carbide.
 5. The apparatus of claim 1, wherein the first composite preform component includes a set of fibers in addition to the extended fibers, the set of fibers less stiff than the extended fibers such that the set of fibers yields its form when the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers.
 6. The apparatus of claim 1, wherein the second composite preform component includes interstitial spacing between a plurality of internal spaces that matches a spacing of the extended fibers from the first composite preform component.
 7. The apparatus of claim 1, further comprising a laminate strip configured to be applied to the joint.
 8. The apparatus of claim 1, wherein the second composite preform component further comprises a plurality of interwoven fibers, and wherein the plurality of extended fibers have sufficient rigidity to act independently from the plurality of interwoven fibers when received into the internal space of a the body of the second composite preform component.
 9. The apparatus of claim 1, wherein the plurality of extended fibers comprises an outer coating.
 10. The apparatus of claim 1, wherein the second end surface comprises a plurality of interstitial openings configured to receive the plurality of extended fibers.
 11. An apparatus comprising: a gas turbine engine ceramic matrix composite component for a gas turbine engine, comprising a first ceramic preform comprising a first end surface and a second ceramic preform comprising a second end surface, wherein the first ceramic preform includes a plurality of first extended fibers having an extended portion that protrudes away from the first end surface, the first extended fibers being received within an internal space of a body of the second ceramic preform, and wherein the first extended fibers are woven into the first ceramic preform but not woven into the second ceramic preform; wherein the second ceramic preform includes a plurality of second extended fibers having an extended portion that protrudes away from the second end surface, the second extended fibers being received within an internal space of a body of the first ceramic preform, and wherein the second extended fibers are woven into the second ceramic preform but not woven into the first ceramic preform; and wherein an interface of the first end surface and the second end surface forms a joint between the first ceramic preform and the second ceramic preform.
 12. The apparatus of claim 11, wherein the second end surface comprises a plurality of interstitial openings configured to receive the plurality of first extended fibers and the first end surface comprises a plurality of interstitial openings configured to receive the plurality of second extended fibers.
 13. The apparatus of claim 11, further comprising a third ceramic preform positioned within the joint, wherein a portion of at least one of the plurality of first extended fibers and the plurality of second extended fibers extend through the third ceramic preform.
 14. The apparatus of claim 13, wherein the third ceramic preform extends outwardly from a plane occupied by the first ceramic preform and the second ceramic preform.
 15. The apparatus of claim 14, wherein the third ceramic preform has a cross-sectional shape of an airfoil.
 16. An apparatus comprising: a gas turbine engine ceramic matrix composite component, comprising a first ceramic preform arranged along a first longitudinal axis and comprising a first end surface and a plurality of extended fibers having an extended portion that protrudes away from the first end surface, and a second ceramic preform arranged along a second longitudinal axis and comprising a second end surface, wherein the extended fibers are received within an internal space of a body of the second ceramic preform, wherein a joint is created between the first ceramic preform and the second ceramic preform at an interface of the first end surface and the second end surface, and wherein the extended fibers are woven into the first ceramic preform, but not woven into the body of the second ceramic preform; and wherein the first longitudinal axis passes through the first end surface and the second longitudinal axis passes through the second end surface.
 17. The apparatus of claim 16, wherein the joint is configured such that first longitudinal axis and the second longitudinal axis occupy a common plane.
 18. The apparatus of claim 16, wherein the joint is configured such that the first longitudinal axis occupies a first plane and the second longitudinal axis occupies a second plane which is skewed from the first plane.
 19. The apparatus of claim 16, wherein the joint is configured such that the first longitudinal axis occupies a first plane and the second longitudinal axis occupies a second plane distinct from the first plane and parallel to the first plane. 